Invention content
The object of the present invention is to provide a kind of aircraft, which improves, is embodied in and is provided simultaneously withPreferable flat winged performance and VTOL performance.
To achieve the above object, the present invention provides a kind of aircraft, and the machine is arranged symmetrically in including fuselage body, twoThe front wing of body body head and two main wings for being arranged symmetrically in fuselage body tail portion, the front wing be lower single-blade, the main wingFor high mounted wing, the tip of a root ratio of the main wing and the front wing is 1:1, and without angle of sweep.
Preferably, main wing ducted fan group, front wing ducted fan group are further included and for driving the main wing ducted fanGroup unitary rotation and the driving front wing ducted fan group unitary rotation, it is described to control the fan control device of thrust vectoringMain wing ducted fan group is rotatably provided in the wing root portion of the main wing, and the front wing ducted fan group is rotatably provided in describedThe wing root portion of front wing.
Preferably, the ducted fan arragement direction in the main wing ducted fan group is parallel with the main wing length direction,Ducted fan arragement direction in the front wing ducted fan group is parallel with the front wing length direction.
Preferably, the tail portion ducted fan group for being rotatably provided in fuselage body tail portion, the tail portion duct wind are further includedFan group controls unitary rotation by the fan control device, and the tail portion ducted fan group is located at main wing duct wind described in two groupsBetween fan group, the ducted fan in the tail portion fan group is arranged along the fuselage body width direction.
Preferably, two side ducted fan groups are further included, the side ducted fan group is two, two sidesThe ducted fan of ducted fan group is arranged symmetrically at left and right sides of the fuselage body, and the side ducted fan group passes through describedFan control device control translation, when the side ducted fan works, the fan control device controls the side to containRoad fan group is moved on the outside of the fuselage body, and when in flat winged state, the fan control device controls the sideDucted fan group is moved to inside the fuselage body.
Preferably, the tail portion ducted fan group includes four ducted fans being sequentially arranged, the side ducted fanGroup includes nine ducted fans being sequentially arranged.
Preferably, the front wing have inverted diherdral, and the end of the front wing be equipped with winglet, the winglet toLower fold.
Preferably, the end of the main wing is equipped with winglet.
Preferably, the fuselage body is equipped with liquid crystal display and the touch screen of human-computer interaction, the fuselage bodyCanopy is transparent canopy.
Preferably, the aspect ratio of the main wing is 7-11, and the area of plane is more than the preceding wing area.
In the above-mentioned technical solutions, aircraft provided by the invention is arranged symmetrically in fuselage sheet including fuselage body, twoThe front wing on body head and two main wings for being arranged symmetrically in fuselage body tail portion, front wing are lower single-blade, and main wing is high mounted wing, main wingTip of a root ratio with front wing is 1:1, and without angle of sweep.
By foregoing description it is found that in the aircraft provided in the application, wing is laid out using front and rear double-vane, is ensureing footEnough areas reduce the demand to hangar and landing site, and front wing is lower single-blade, and main wing is the tip of a root of high mounted wing, main wing and front wingThan being 1:1, and without angle of sweep, promote flight pneumatic efficiency, play the flat winged and VTOL performance of tradeoff, have compared with Gao PingfeiThe Flight Vehicle Design of performance and VTOL performance.
Specific embodiment
The core of the present invention is to provide a kind of aircraft, which improves, and is embodied in and is provided simultaneously withPreferable flat winged performance and VTOL performance.
In order to which those skilled in the art is made to more fully understand technical scheme of the present invention, below in conjunction with the accompanying drawings and embodiment partyThe present invention is described in further detail for formula.
It please refers to Fig.1 to Fig. 4, in a kind of specific embodiment, the aircraft that the specific embodiment of the invention provides includes1, two front wing 2 for being arranged symmetrically in 1 head of fuselage body of fuselage body and two masters for being arranged symmetrically in 1 tail portion of fuselage bodyThe wing 3, front wing 2 are lower single-blade, and main wing 3 is high mounted wing, and the tip of a root ratio of main wing 3 and front wing 2 is 1:1, and without angle of sweep.It is preferred thatFront wing 2 and main wing 3 are rectangular wing, with obtain low cruise (<0.3 Mach) when higher pneumatic efficiency, convenient for facilitating lifeProduction and maintenance.
By foregoing description it is found that in the aircraft provided in the application specific embodiment, wing uses front and rear double-vaneLayout is ensureing enough area, reduces the demand to hangar and landing site, and front wing 2 is lower single-blade, and main wing 3 is high mounted wing, mainThe wing 3 selects the high mounted wing of interference drag minimum, while reduces the influence of front wing 2 and front-mounted engine wake flow to wing, main wing 3Tip of a root ratio with front wing 2 is 1:1, and without angle of sweep, promote flight pneumatic efficiency, play the flat winged and VTOL of tradeoffCan, have the Flight Vehicle Design of higher flat winged performance and VTOL performance.
Further, which further includes main wing ducted fan group 8, front wing ducted fan group 7 and for main wing to be driven to contain7 unitary rotation of 8 unitary rotation of road fan group and driving front wing ducted fan group, to control the fan control device of thrust vectoring,Specifically, main wing ducted fan group 8 and front wing ducted fan group 7 can drive unitary rotation to change by independently arranged motorThe direction of thrust vectoring, motor setting is on fuselage body 1.Main wing ducted fan group 8 is rotatably provided in the wing root of main wing 3Portion, front wing ducted fan group 7 are rotatably provided in the wing root portion of front wing 2.Further, it is preferable that the culvert in main wing ducted fan group 8Road fan arragement direction is parallel with 3 length direction of main wing, the ducted fan arragement direction in front wing ducted fan group 7 and front wing 2Length direction is parallel.Specifically, main wing ducted fan group 8 and front wing ducted fan group 7 include three ducts being sequentially arrangedFan.Specifically, the blade rotary centerline of ducted fan is vertical with 3 length direction of main wing in main wing ducted fan group 8, main wingDucted fan group 8 is arranged in the rear of main wing 3.The blade rotary centerline of ducted fan and front wing 2 in front wing ducted fan group 7Length direction is vertical, and front wing ducted fan group 7 is arranged in the rear of front wing 2.
Further, which further includes the tail portion ducted fan group 6 for being rotatably provided in 1 tail portion of fuselage body, wherein,Tail portion ducted fan group 6 can be driven by motor and be rotated integrally, and change thrust vectoring direction, it is preferable that tail portion ducted fan group 6It is arranged on the rear end of 1 tail portion of fuselage body, the blade rotary centerline and fuselage body of ducted fan in tail portion ducted fan group 61 width direction is vertical, and tail portion ducted fan group 6 is controlled by fan control device and rotated, and tail portion ducted fan group 6 is located at two groupsBetween main wing ducted fan group 8, the ducted fan in the fan group of tail portion is arranged along 1 width direction of fuselage body.Specifically, ductFan is the small-sized ducted fan of 30cm, and separate unit fan maximum thrust 400N certainly, can be according to actual conditions in actual designMatch the ducted fan of different thrusts and size.
Further, which further includes two side ducted fan groups 4, and side ducted fan group 4 is two, twoThe ducted fan of side ducted fan group 4 is arranged symmetrically in 1 left and right sides of fuselage body, and side ducted fan group 4 passes through fanControl device control translation, when side ducted fan 4 works, fan control device control side ducted fan group 4 moves to4 outside of fuselage body, when in flat winged state, fan control device control side ducted fan group 4 moves to fuselage body 4It is internal.Its influence to wing aerodynamic efficiency is reduced by main wing ducted fan group 8, front wing ducted fan group 7.And with aileron/Elevator is combined, and reduces the quantity of moving component, reduces complex degree of structure.Tail portion ducted fan group 6 is installed in fuselage1 tail portion upper surface of ontology, air intake duct accelerate 1 boundary layer of fuselage body close to fuselage body 1, reduce boundary layer thickness,So as to reduce frictional resistance.Engine wake flow accelerates to flying the low speed flow in tail, reduces form drag.Power clothOffice, the wing root portion of main wing 3 and the wing root portion of front wing 2 are separately mounted to by main wing ducted fan group 8, front wing ducted fan group 7, are led toThe negative effect that downwash flow generates wing can be reduced by crossing change ducted fan air intake duct and spout angle.
Preferably, tail portion ducted fan group 6 includes four ducted fans being sequentially arranged, preferably tail portion ducted fan group 6Ducted fan along 1 width direction of fuselage body arrange, side ducted fan group 4 include nine ducted fans being sequentially arranged,It is preferred that the ducted fan of side ducted fan group 4 is arranged along 1 length direction of fuselage body.
Further, front wing 2 has inverted diherdral, and the end of front wing 2 is equipped with winglet, and winglet is turned over downwards.BeforeThe wing 2 selects lower single-blade, ensures the visual field of cockpit, and can reduce influence of the flow perturbation to main wing 3.Inverted diherdral make air-flow generate toThe trend that ventral is gathered can improve the lift and pneumatic efficiency of fuselage sections by a small margin.Winglet is turned over downwards, furtherThe position of tip vortex core low-pressure area is reduced, reduces its negative effect to main wing 3.What front wing 2 generated rotates counterclockwiseVortex makes wing panel in main wing 3 by downwash flow, wing panel pneumatic efficiency in main wing 3 be caused to decline, induced drag increases.Outside main wing 3Wing panel can be improved the pneumatic efficiency of aircraft by upper gas washing stream in a certain range, reduce induced drag.
Preferably, the end of main wing 3 is equipped with winglet.3 outer panel of main wing is raised at the upper counterangle, is avoided and 2 wing of front wingThe low-pressure area contact of point vortex core, and improve roll stability.The outer panel of main wing 3 does not install ducted fan, and installs the wing additionalTip winglet, the improved efficiency that upper gas washing stream is brought maximize.
The aircraft that the application provides provides lift, wherein 16 using 34 ducted fans in total as hovering configurationDucted fan is mounted on tail and upper surface of the airfoil, i.e. main wing ducted fan group 8, front wing ducted fan group 7 and tail portion duct windFan group 6, it is flat that thrust is provided when flying, when hovering the spout that verts lift is provided downwards.By the angle for changing this 16 ducted fansThe gesture stability of aircraft is realized with thrust.18 ducted fans are mounted on 1 both sides of fuselage body, i.e. side ducted fan group 4,Flat withdraw when flying improves pneumatic efficiency, and when hovering is unfolded.Because only being used in hovering, air intake duct and spout are pushed away using raising is staticThe design of power and efficiency of energy utilization.Except non-extreme conditions, the ducted fan of side ducted fan group 4 is not involved in gesture stability.
It is preferred that fuselage body 1 is equipped with liquid crystal display and the touch screen of human-computer interaction, the canopy of fuselage body 1 areTransparent canopy.Pass through liquid crystal display so that data appearance form is more flexible clear.By touch screen operation, reduceOperation difficulty, human-computer interaction are more smooth.In order to improve riding comfort, it is preferable that preferably, the seat in 1 cockpit of fuselage bodyChair is clad type seat, and improves safety in emergency circumstances.
On the basis of above-mentioned each scheme, it is preferable that the aspect ratio of main wing 3 is 7-11, and 3 area of main wing is more than 2 area of front wing.In a kind of specific embodiment, such as in twin, the downward projection area of main wing 3 and front wing 2 is 10m^2.Main wing 3Area is much larger than front wing 2, and the quiet of aircraft is may insure in the case of correctly configuration 2 established angle of center of gravity and main wing 3 and front wingStablize aerodynamic characteristic.Special designing fuselage cross-section aerofoil profile reduces the displacement of the aerodynamic center when the angle of attack changes, it is ensured that aircraftStatic-stability characteristic.Realize VTOL, high-performance cruise, low noise, zero-emission operation.It is preferred that the spanwise length of main wing 3 is8.6m, aircraft clear height are 1.6m, and the height of cockpit is 2.0m, is highly 1.2m, and the length of fuselage body 1 is 5.9m.Certainly,In use, can be according to aircraft specific requirements in actual design, and then adjust each data of aircraft.
Each embodiment is described by the way of progressive in this specification, the highlights of each of the examples are with otherThe difference of embodiment, just to refer each other for identical similar portion between each embodiment.
The foregoing description of the disclosed embodiments enables professional and technical personnel in the field to realize or use the present invention.A variety of modifications of these embodiments will be apparent for those skilled in the art, it is as defined hereinGeneral Principle can be realized in other embodiments without departing from the spirit or scope of the present invention.Therefore, it is of the inventionThe embodiments shown herein is not intended to be limited to, and is to fit to and the principles and novel features disclosed herein phase oneThe most wide range caused.